US9885481B2 - Sequential combustion with dilution gas mixer - Google Patents

Sequential combustion with dilution gas mixer Download PDF

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US9885481B2
US9885481B2 US14/445,162 US201414445162A US9885481B2 US 9885481 B2 US9885481 B2 US 9885481B2 US 201414445162 A US201414445162 A US 201414445162A US 9885481 B2 US9885481 B2 US 9885481B2
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dilution
gas
burner
fuel
dilution gas
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US20150047365A1 (en
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Michael DUESING
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Ansaldo Energia Switzerland AG
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Ansaldo Energia Switzerland AG
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F23R3/346—Feeding into different combustion zones for staged combustion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/26—Controlling the air flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/22—Fuel supply systems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/22—Fuel supply systems
    • F02C7/228—Dividing fuel between various burners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03341—Sequential combustion chambers or burners

Definitions

  • the invention refers to a sequential combustor arrangement for a gas turbine with admixing dilution gas into the sequential combustor arrangement.
  • the invention additionally refers to a method for operating a gas turbine with admixing dilution gas into a sequential combustor arrangement.
  • emission limit values and overall emission permits are becoming more stringent, so that it is required to operate at lower emission values, keep low emissions also at part load operation and during transients, as these also count for cumulative emission limits.
  • State-of-the-art combustion systems are designed to cope with a certain variability in operating conditions, e.g. by adjusting the compressor inlet mass flow or controlling the fuel split among different burners, fuel stages or combustors. However, this is not sufficient to meet the new requirements.
  • the object of the present disclosure is to propose a sequential combustor arrangement with a burner comprising means for admixing dilution gas and the second fuel between the first combustion chamber and the second combustion chamber.
  • a “dilution burner” has to provide the proper inlet flow conditions for the second combustion chamber.
  • the hot gases are cooled to predetermined hot gas temperatures.
  • velocity distribution, oxygen and fuel content can be conditioned (e.g. controlled to a prescribed profile) for the second combustion chamber with proper admixing of dilution gas.
  • Deviations from prescribed inlet temperatures may result in high emissions (e.g. NOx, CO, and unburned hydrocarbons) and/or flashback in the dilution burner. Flashback and NOx are induced by the reduced self-ignition time for the injected fuel due to a high inlet gas temperature or high oxygen concentration, which causes earlier ignition (leading to flashback) or reduced time for fuel air mixing resulting in local hot spots during combustion and consequently increased NOx emission. Low temperature regions can cause CO emissions, due to the increased self-ignition time. This can reduce the time for CO to CO2 burnout, and a reduced local flame temperature, which can further slowdown the CO to CO2 burnout. Finally local hot spots may lead to overheating in certain regions downstream of the mixer.
  • high emissions e.g. NOx, CO, and unburned hydrocarbons
  • flashback and NOx are induced by the reduced self-ignition time for the injected fuel due to a high inlet gas temperature or high oxygen concentration, which causes earlier ignition (leading to flashback) or reduced time
  • Dilution gas can for example be compressed air or a mixture of air and flue gases of a gas turbine. Also compressed flue gases can be used as dilution gas.
  • a sequential combustor arrangement comprises a first burner, a first combustion chamber, a dilution burner for admixing a dilution gas and a second fuel, and a second combustion chamber arranged sequentially in a fluid flow connection.
  • the dilution burner comprises a dilution-gas-fuel-admixer for admixing a dilution gas and a second fuel to the first combustor combustion products leaving the first combustion chamber during operation.
  • the first fuel and second fuel can be the same type of fuel, e.g. both gaseous or both liquid fuel and come from the same source or can be different fuel types provided from different fuel sources.
  • the dilution-gas-fuel-admixer has at least one streamlined body which is arranged in the dilution burner with at least one fuel nozzle for introducing the at least one fuel into the dilution burner.
  • the streamlined body has a streamlined cross-sectional profile which extends with a longitudinal direction perpendicularly or at an inclination to a main flow direction prevailing in the dilution burner. Upstream of the at least one fuel nozzle the at least one streamlined body of the dilution-gas-fuel-admixer comprises a dilution gas opening for admixing dilution gas into the first combustor combustion products.
  • the dilution gas opening is dimensioned such that during operation the mass flow ratio of the first combustor combustion products to the mass flow of dilution gas admixed through the dilution gas opening is in a range of 0.5 to 2.
  • the dilution gas opening is dimensioned such that during operation the mass flow ratio in a range of 0.7 to 1.5, and most preferably in the range of 0.9 to 1.1.
  • the dilution gas opening is directed parallel to the main flow direction of the first combustor combustion products leaving the first combustor during operation.
  • the dilution gas opening is directed to release dilution gas parallel to the main flow at the location of the dilution gas opening.
  • the ratio of the flow area for first combustor combustion products at the location of the dilution gas openings to the flow area of dilution gas opening is in the range of 1 to 10.
  • the ratio of flow areas is in the range of 2 to 7 and most preferably in the range of 4 to 6.
  • the dilution-gas-fuel-admixer has at least two dilution gas openings for admixing dilution gas into the first combustor combustion products.
  • the at least two dilution gas openings for admixing dilution gas into the first combustor combustion products are formed as slots, which extend from lateral surfaces of the streamlined body of the dilution-gas-fuel-admixer towards the flow area of the first combustor combustion products, i.e. normal to the longitudinal extension of the stream lined body.
  • the height of the slots can be determined as a function of the temperature distribution and/or velocity distribution of the first combustor combustion products entering the dilution burner.
  • the slot height can be basically proportional to the temperature difference between the hot gas at the corresponding position of the slot and the temperature of the dilution gas. Since the dilution gas admixed through the slot is proportional to the slot height the cooling effect of the dilution gas is proportional to the slot height and an inhomogeneous temperature profile at the exit of the first combustion chamber can be equalized with a matched height distribution; e.g. a slot with a large height in regions of high temperature and a slot a small height in a region of low temperature.
  • the height of the slots can determined as a function of the position in the longitudinal direction of the streamlined body.
  • the height distribution can be a simple linear function with the height increasing from one end of the slot to the other. It can be any curve or have a reduced height towards the end of the slot, close the side walls of the dilution burner because the temperature might already be reduced due to wall cooling in the dilution burner or the combustion chamber.
  • a vortex generator is arranged on at least one lateral surfaces of the streamlined body.
  • the vortex generators can for example be of triangular shape with a triangular lateral surface converging with the lateral surface upstream of the vortex generator, and two side surfaces essentially perpendicular to a central plane of the streamlined body.
  • the two side's surfaces converge at a trailing edge of the vortex generator. This trailing edge is typically just upstream of the corresponding fuel nozzle.
  • the trailing edges of the streamlined body are provided with at least two lobes in opposite transverse directions with reference to a central plane of the streamlined body.
  • the width of cross section of the streamlined body (normal to the flow direction of the main flow at the location of the dilution gas opening) is reduced to increase the flow area in the dilution burner.
  • the ratio of the sum of cross section of the dilution gas openings to the area of the largest cross section of the streamlined burner downstream of the dilution gas openings can for example be in the order of 0.1 to 2 or even larger. According to one embodiment this ratio is in the range of 0.5 to 1.5.
  • Such a gas turbine comprises at least a compressor, a sequential combustor arrangement and a turbine, wherein the sequential combustor arrangement has a first burner, a first combustion chamber, a dilution burner with a dilution-gas-fuel-admixer, and a second combustion chamber arranged sequentially in a fluid flow connection.
  • the first combustor combustion products, second fuel, and dilution gas are at least partly mixed in the dilution-gas-fuel-admixer.
  • the second fuel is introduced into the dilution burner with a dilution-gas-fuel-admixer having at least one streamlined body which is arranged in the dilution burner.
  • the second fuel can be injected through at least one fuel nozzle from the streamlined body.
  • the at least one streamlined has a streamlined cross-sectional profile which extends with a longitudinal direction perpendicularly or at an inclination to a main flow direction prevailing in the dilution burner. From the at least one streamlined body dilution gas is admixed via at least one dilution gas opening into the first combustor combustion products upstream of the at least one fuel nozzle.
  • the mass flow ratio of the mass flow of first combustor combustion products entering the dilution burner to the mass flow of dilution gas admixed through the dilution gas opening is in the range of 0.5 to 2.
  • the ratio is in the range of 0.7 to 1.5, and most preferably the ratio is in a range of 0.9 to 1.1.
  • the dilution gas is injected into the dilution gas burner through the dilution gas opening in a direction within a maximum deviation of 20° to the flow direction of the main flow direction of the first combustor combustion products at the point of injection.
  • the dilution gas is injected into the dilution gas burner through the dilution gas opening parallel to the flow direction of the main flow of the first combustor combustion products.
  • the dilution gas is injected into the dilution gas burner through the dilution gas opening with the same average velocity as the average flow velocity of the first combustor combustion products at the point of injection or within a maximum deviation of 30% to the average flow velocity of the first combustor combustion products at the point of injection.
  • dilution gas and combustion products of the first combustor can flow parallel to each other along the streamlined body. Downstream of the openings for admixing dilution gas the fuel can be injected practically into the dilution gas, and all three fluids: combustion products of the first combustor, dilution gas and fuel can be mixed in one step.
  • vortex generators can be arranged on at least one lateral surfaces of the streamlined body.
  • the trailing edges of the streamlined body can be provided with at least two lobes in opposite transverse directions relative to a reference to a central plane of the streamlined body.
  • the dilution gas is admixed into the first combustor combustion products through at least two dilution gases opening, which are formed as slots.
  • Each of these slots extends from a lateral surface of the streamlined body of the dilution-gas-fuel-admixer towards the flow area of the first combustor combustion products (i.e. normal to the lateral surface of the streamlined body).
  • the mass flow distribution of injected dilution gas in longitudinal direction of the streamlined body is determined as a function of the temperature distribution and/or velocity distribution of the first combustor combustion products entering the dilution burner. Typically more dilution gas is injected into regions with higher temperature than into a region with a lower temperature.
  • the mass flow distribution of injected dilution gas in longitudinal direction of the streamlined body is determined as a function of the position along the longitudinal direction of the streamlined body.
  • Cooling of the streamlined body can be required. In particular upstream of the location of the dilution gas openings the streamlined body is exposed to the hot combustion products of the first combustor.
  • a cooling gas is used to cool external surface of the streamlined body.
  • most of the fluid added from the streamlined body is dilution gas.
  • the ratio of dilution gas to cooling gas is greater than 2; preferably the ratio is greater than 5, or even up to 20 or 50. Cooling and dilution gas can have the same composition and can come from the same source.
  • a local high oxygen concentration can have a similar effect as a local high temperature, e.g. leading to fast reaction, consequently to reduce the available time for mixing before self-ignition occurs, high combustion temperatures, increased NOx emissions and possibly flash back.
  • a local low oxygen concentration can have a similar effect as a local low temperature, e.g. leading to slow reaction, consequently to increased CO and UHC (unburned hydrocarbon) emissions. Therefore the admixing of dilution gas can be distributed to adjust the oxygen concentration in the gas leaving the dilution burner.
  • the dilution-gas-fuel-admixer can also be combined with dampers or as connecters to damping volumes as described in the European patent application EP12189685, which is incooperated by reference.
  • the gas turbine can include a flue gas recirculation system, in which a part of the flue gas leaving the turbine is admixed to the compressor inlet gas of the gas turbine.
  • the combination of combustors can be disposed as follows:
  • first combustor so called EV burner as known for example from the EP 0 321 809 or AEV burners as known for example from the DE195 47 913 can for example be used.
  • a BEV burner comprising a swirl chamber as described in the European Patent application EP12189388.7, which is incorporated by reference, can be used.
  • a flamesheet combustor as described in US2004/0211186, which is incorporated by reference, can be used as first combustor.
  • FIG. 1 shows a gas turbine with a sequential combustion arrangement with a first burner, first combustion chamber, a mixer for admixing dilution gas, a second burner, and a second combustion chamber;
  • FIG. 2 shows a gas turbine with a sequential combustion arrangement in annular architecture with a first burner, first combustion chamber, a dilution burner, and a second combustion chamber;
  • FIG. 3 shows a gas turbine with a sequential combustion arrangement in annular architecture with a first burner, counter flow cooling of the first combustion chamber, a first combustion chamber, a dilution burner, and a second combustion chamber;
  • FIG. 4 shows a gas turbine with a sequential combustion arrangement in can architecture with a first burner, first combustion chamber, a dilution burner, and a second combustion chamber;
  • FIG. 5 shows a dilution burner with a dilution-gas-fuel-admixer with vortex generators and carrier gas injection
  • FIG. 6 shows a dilution burner with a dilution-gas-fuel-admixer and a thin trailing edge
  • FIG. 7 shows a dilution-gas-fuel-admixer with slots for admixing dilution gas on both sides of the streamlined body
  • FIG. 8 shows a dilution burner with a dilution-gas-fuel-admixer with vortex generators, two axial staged gas openings on each side of the streamlined body and carrier gas injection;
  • FIG. 9 shows a perspective view of dilution-gas-fuel-admixer with vortex generators, cooling gas injection from the trailing edge and carrier gas injection;
  • FIG. 10 shows a perspective view of dilution-gas-fuel-admixer with lobes for vortex generation and carrier gas injection.
  • FIG. 1 shows a gas turbine 1 with a sequential combustor arrangement 4 . It comprises a compressor 3 , a sequential combustor arrangement 4 , and a turbine 5 .
  • the sequential combustor arrangement 4 comprises a first burner 10 , a first combustion chamber 11 , and a mixer 12 for admixing a dilution gas 32 to the hot gases leaving the first combustion chamber 11 during operation. Downstream of the mixer 12 the sequential combustor arrangement 4 further comprises a second burner 13 , and a second combustion chamber 14 . The first burner 10 , first combustion chamber 11 , mixer 12 , second burner 13 and second combustion chamber 14 are arranged sequentially in a fluid flow connection.
  • the sequential combustor arrangement 4 is housed in a combustor casing 31 .
  • the compressed gas 8 leaving the compressor 3 passes through a diffusor 30 for at least partly recovering the dynamic pressure of the gas leaving the compressor.
  • the sequential combustor arrangement 4 further comprises a first combustion chamber cooling zone with a first cooling channel 15 which is delimited by the first combustion chamber wall 24 and a first jacket 20 , which is enclosing the first combustion chamber wall 24 . It comprises a mixer cooling zone with a second cooling channel 16 which is delimited by a mixer wall 25 and a second jacket 21 , which is enclosing the mixer wall 25 . It comprises a second burner cooling zone with a third cooling channel which is delimited by a second burner wall 26 and a third jacket 22 , which is enclosing the second burner wall 26 . It also comprises a second combustion chamber cooling zone with a fourth cooling channel 18 , which is delimited by a second combustion chamber wall 27 , and a fourth jacket 23 , which is enclosing the second combustion chamber wall 27 .
  • Compressed gas 8 is fed into the first cooling channel 15 as cooling gas 33 at an upstream end (relative to the hot gas flow direction) and flows through the first cooling channel 15 parallel to the main flow direction of the hot gas flow in the first combustion chamber 11 .
  • the cooling gas 33 After passing through the first cooling channel 15 the cooling gas 33 enters the second cooling channel for cooling the mixer. After at least partly cooling the mixer the cooling gas 33 is fed into the dilution gas inlet 19 and admixed to the hot gas as dilution gas 32 in the mixer 12 .
  • Compressed gas 8 is also fed into the fourth cooling channel 18 as cooling gas 33 at a downstream end (relative to the hot gas flow direction) and flows in counter flow to the main flow direction of the hot gas flow in the second combustion chamber 14 .
  • the cooling gas 33 After passing through the fourth cooling channel 18 the cooling gas 33 enters the third cooling channel 17 at a downstream end (relative to the hot gas flow direction) and flows in counter flow to the main flow direction of the hot gas flow in the second burner 13 .
  • the cooling gas 33 is fed to the second burner 13 .
  • the cooling gas 33 can for example be fed to the second burner 13 as cooling gas, e.g. as film cooling gas or diffusion cooling. Part of the cooling gas 33 can already be fed to the hot gas 9 in the second combustion chamber 14 during cooling of the second combustion chamber wall 27 (not shown).
  • a first fuel 28 can be introduced into the first burner 10 via a first fuel injection, mixed with compressed gas 8 which is compressed in the compressor 3 , and burned in the first combustion chamber 11 .
  • Dilution gas 32 is admixed in the subsequent mixer 12 .
  • a second fuel 29 can be introduced into the second burner 13 via a second fuel injector 51 , mixed with hot gas leaving the mixer 12 , and burned in the second combustion chamber 14 .
  • the hot gas leaving the second combustion chamber 14 is expanded in the subsequent turbine 5 , performing work.
  • the turbine 5 and compressor 3 are arranged on a shaft 2 .
  • the remaining heat of the exhaust gas 7 leaving the turbine 5 can be further used in a heat recovery steam generator or boiler (not shown) for steam generation.
  • compressed gas 8 is admixed as dilution gas 32 .
  • compressor gas 8 is compressed ambient air.
  • the compressor gas is a mixture of ambient air and recirculated flue gas.
  • the gas turbine system includes a generator (not shown) which is coupled to a shaft 2 of the gas turbine 1 .
  • the gas turbine 1 further comprises a cooling system for the turbine 5 , which is also not shown as it is not subject of the invention.
  • FIGS. 2 to 4 Different exemplary embodiments of the sequential combustor arrangement with a dilution burner are shown in FIGS. 2 to 4 . Details of different exemplary embodiments of the dilution burner are shown in FIGS. 5 to 10 .
  • FIG. 2 differs from the combustor arrangement of FIG. 1 in that the mixer 12 and second burner 13 are replaced by a dilution burner 35 .
  • the dilution burner 35 comprises dilution burner walls 36 delimiting the hot gas path, and a dilution-gas-fuel-admixer 34 arranged in the hot gas path of the dilution burner 35 .
  • the hot first combustor combustion products 37 enter directly into the dilution burner 35 without any prior cooling.
  • the Second fuel 29 and dilution gas 32 is supplied via the dilution-gas-fuel-admixer 34 .
  • the dilution gas 32 is feed into the dilution-gas-fuel-admixer 34 via a dilution gas feed 46 from the third cooling channel 17 enclosing the dilution burner 35 .
  • the dilution gas 32 can also be supplied from other sources as for example directly from the compressor diffusor 30 or from the first cooling channel 15 .
  • compressed gas 8 is fed into the fourth cooling channel 18 as cooling gas 33 at a downstream end (relative to the hot gas flow direction) and flows in counter flow to the main flow direction of the hot gas flow in the second combustion chamber 14 .
  • the cooling gas 33 After passing through the fourth cooling channel 18 the cooling gas 33 enters the third cooling channel 17 at a downstream end (relative to the hot gas flow direction) and flows in counter flow to the main flow direction of the hot gas flow in the dilution burner 35 .
  • the cooling gas 33 is fed to the dilution burner 35 .
  • the cooling gas is used as dilution gas 32 .
  • FIG. 3 is based on FIG. 2 .
  • the cooling gas 33 cools the first combustion chamber 11 in a counter flow arrangement. After cooling the first combustion chamber 11 the cooling gas 33 enters a burner hood which guides the cooling gas 33 into the first burner 10 .
  • FIG. 4 is based on FIG. 2 .
  • the dilution burner and cooling scheme is unchanged but a sequential combustion arrangement in a can architecture and with a flame sheet burner as first burner 10 is shown.
  • a plurality sequential combustion arrangement in a can architecture is arranged circumferentially spaced on a radius around the axis of the gas turbine (not shown).
  • FIG. 5 shows a cross section of a dilution burner 35 with a dilution-gas-fuel-admixer 34 interposed between two side walls 36 of the dilution burner 35 .
  • the dilution-gas-fuel-admixer 34 comprises a streamlined body 42 with a leading edge section 47 and a trailing edge section 48 , as well as vortex generators 41 attached to the lateral walls of the streamlined body 42 .
  • dilution gas openings 44 are arranged, facing in a downstream direction of the flow of the first combustor combustion products 37 for injecting the dilution gas 32 in the same direction as the main flow.
  • the width of cross section of the streamlined body is reduced to increase the flow area in the dilution burner by the flow area A d of dilution gas opening 44 .
  • the flow area in the dilution burner was equal to the flow area for first combustion products A c .
  • cooling gas 45 can be injected through cooling holes.
  • a film cooling can be applied for the leading edge section 47 .
  • ducts are provided to feed gaseous fuel 38 and liquid fuel 39 to the fuel injection nozzles 43 for injecting the fuel 38 , 39 .
  • the nozzles 43 are arranged at the trailing edge of the streamlined body 42 .
  • carrier gas 40 can be injected from opening adjacent to the fuel nozzles 43 .
  • To enhance mixing vortex generators 41 are extending from the lateral sides of the streamlined body 42 .
  • FIG. 6 is based on FIG. 5 . It differs from the example of FIG. 4 in that it has no cooling or carrier air is injected at the trailing edge. Without the air injection the trailing edge section 48 and in particular the trailing edge can be designed thinner thereby reducing losses.
  • the second combustion chamber 14 which is arranged downstream of the dilution burner 35 is indicated in FIG. 6 .
  • the cross section of the flow path is increasing towards the dilution burner 35 for flame stabilization.
  • FIG. 7 shows an embodiment of a dilution burner 35 with a rectangular flow cross section.
  • dilution burners can be arranged circumferentially around the axis of a gas turbine with a radial direction r pointing away from the axis.
  • the longitudinal direction of the streamlined body 42 is parallel to the radial direction r when installed in the gas turbine.
  • the cross section is shown from the downstream end of the dilution burner 35 .
  • the dilution-gas-fuel-admixer 34 of this example has only one fuel nozzle 43 for injecting either gaseous or liquid fuel 38 , 39 .
  • the trailing edge section 48 is extending on both sides of the nozzle 43 .
  • a dilution gas opening 44 is arranged on both sides of the trailing edge section 48 .
  • the dilution gas opening 44 has the form of a slot extending in radial direction r.
  • the height h of the slot is linearly increasing from an inner slot height h i to an outer slot height h o .
  • the slot height is determined by the downstream end of the leading edge section 47 .
  • FIG. 8 shows a cross section of a dilution burner 35 with a dilution-gas-fuel-admixer 34 interposed between two side walls 34 of the dilution burner 35 similar to FIG. 5 .
  • the dilution-gas-fuel-admixer 34 comprises gas openings 44 a and 44 b in an axially staged arrangement, facing in a downstream direction of the flow of the first combustor combustion products 37 for injecting the dilution gas 32 in the same direction as the main flow.
  • FIG. 9 shows a perspective view of dilution-gas-fuel-admixer 34 with vortex generators. It is similar to the embodiment shown in FIG. 5 . However, in this example fuel 38 , 39 is injected from circular, respectively annular fuel nozzles 43 arranged at the trailing edge 48 . In addition cooling gas 45 is injected from a slot which is extending along the trailing edge 48 of the streamlined body 42 . Carrier gas 40 can be injected via an annular opening, which is arranged coaxially around the fuel nozzles 43 . To enhance mixing of fuel 38 , 39 with the dilution gas 32 and first combustor combustion products 37 vortex generators 41 are arranged upstream of the fuel nozzles 43 on the lateral walls 49 of the streamlined body 42 .
  • a section of the dilution burner wall 36 is indicated.
  • the streamlined body 42 of the dilution-gas-fuel-admixer 34 extends normal to the dilution burner wall 36 into the flow path of the dilution burner.
  • FIG. 10 shows a perspective view of another embodiment of a dilution-gas-fuel-admixer 34 .
  • this embodiment no vortex generators extend from the streamlined body.
  • the streamlined body comprises lobes 50 in opposite transverse directions with reference to a central plane 52 of the streamlined body 42 for vortex generation.
  • EV, AEV or BEV burners can be used for can as well as for annular architectures.
  • the mixing quality of the mixer 12 is crucial for a stable clean combustion since the burner system of the second combustion chamber 14 requires a prescribed inlet conditions.
  • cooling gas and the dilution gas can be re-cooled in a cooling gas cooler before use as cooling gas, respectively as dilution gas.

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EP13180583.0A EP2837888A1 (fr) 2013-08-15 2013-08-15 Combustion séquentielle avec un mélangeur de gaz de dilution
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US11002190B2 (en) * 2016-03-25 2021-05-11 General Electric Company Segmented annular combustion system
US11156164B2 (en) 2019-05-21 2021-10-26 General Electric Company System and method for high frequency accoustic dampers with caps
US11174792B2 (en) 2019-05-21 2021-11-16 General Electric Company System and method for high frequency acoustic dampers with baffles

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EP3306197B1 (fr) 2016-10-08 2020-01-29 Ansaldo Energia Switzerland AG Injecteur bi-carburant pour un brûleur séquentiel d'une turbine à gaz à combustion séquentielle
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US20180080654A1 (en) * 2012-08-24 2018-03-22 Ansaldo Energia Switzerland AG Sequential combustion with dilution gas mixer
US10634357B2 (en) * 2012-08-24 2020-04-28 Ansaldo Energia Switzerland AG Sequential combustion with dilution gas mixer
US11002190B2 (en) * 2016-03-25 2021-05-11 General Electric Company Segmented annular combustion system
US11156164B2 (en) 2019-05-21 2021-10-26 General Electric Company System and method for high frequency accoustic dampers with caps
US11174792B2 (en) 2019-05-21 2021-11-16 General Electric Company System and method for high frequency acoustic dampers with baffles

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EP2837889A1 (fr) 2015-02-18
JP2015036618A (ja) 2015-02-23
KR20150020116A (ko) 2015-02-25
EP2837889B1 (fr) 2019-12-25
JP5875647B2 (ja) 2016-03-02
EP2837888A1 (fr) 2015-02-18
US20150047365A1 (en) 2015-02-19
KR101627523B1 (ko) 2016-06-13
CN104373960A (zh) 2015-02-25

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